A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.


    Access

    Download


    Export, share and cite



    Title :

    Levered counterweight feathering system



    Publication date :

    2023-10-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



    Levered suspension

    Bound, R.H. | Engineering Index Backfile | 1944


    Blade feathering and feathering hinges

    Baumgartl, P. | Engineering Index Backfile | 1952


    Levered connector extractor

    Takahashi, Ted H. | NTRS | 1989


    SEMI-LEVERED SHRINK LANDING GEAR

    DAHL BRUCE A / SAKURAI SEIYA | European Patent Office | 2023

    Free access

    FEATHERING HORIZONTAL FINS

    AKHAPKIN SERGEJ SERGEEVICH | European Patent Office | 2018

    Free access